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NACA 63(3)-218 (naca633218-il)

NACA 63(3)-218 - NACA 63(3)-218 airfoil


Airfoil naca633218-il
Details Dat file Parser  
(naca633218-il) NACA 63(3)-218
NACA 63(3)-218 airfoil
Max thickness 18% at 34.9% chord.
Max camber 1.1% at 24.9% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
NACA 63(3)-218
1.00000     0.00000
0.95016     0.00664
0.90034     0.01501
0.85049     0.02459
0.80059     0.03486
0.75064     0.04544
0.70062     0.05594
0.65055     0.06597
0.60042     0.07526
0.55023     0.08351
0.50000     0.09045
0.44973     0.09577
0.39943     0.09916
0.34911     0.10030
0.29880     0.09884
0.24850     0.09949
0.19822     0.08842
0.14801     0.07895
0.09788     0.06581
0.07288     0.05728
0.04796     0.04673
0.02319     0.03285
0.01096     0.02319
0.00617     0.01778
0.00382     0.01449
0.00000     0.00000
0.00618     -0.01349
0.00883     -0.01638
0.01404     -0.02105
0.02681     -0.02913
0.05204     -0.04041
0.07712     -0.04880
0.10212     -0.05547
0.15199     -0.06549
0.20178     -0.07250
0.25150     -0.07704
0.30120     -0.07940
0.35089     -0.07970
0.40057     -0.07774
0.45027     -0.07387
0.50000     -0.06839
0.54977     -0.06161
0.59958     -0.05384
0.64945     -0.04537
0.69938     -0.03650
0.74936     -0.02754
0.79941     -0.01894
0.84951     -0.01113
0.89966     -0.00467
0.94984     -0.00032
1.00000     0.00000
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Selig format dat file

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Polars for NACA 63(3)-218 (naca633218-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca633218-il50,000922.2 at α=11°Mach=0 Ncrit=9Xfoil predictionDetails
   naca633218-il50,000521.8 at α=10.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca633218-il100,000943 at α=8.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca633218-il100,000538.8 at α=8°Mach=0 Ncrit=5Xfoil predictionDetails
   naca633218-il200,000951.9 at α=9°Mach=0 Ncrit=9Xfoil predictionDetails
   naca633218-il200,000549.6 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca633218-il500,000967.8 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca633218-il500,000563.9 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca633218-il1,000,000981.6 at α=8°Mach=0 Ncrit=9Xfoil predictionDetails
   naca633218-il1,000,000575.9 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
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